Calculation of Enthalpy-Entropy Diagrams for Rocket Propellant Systems

Author: White, Richard Street

Year: 1948

Degree: Engineer's thesis

Advisor: Unknown, Unknown

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/PGDK-YH67

Abstract

It is the purpose of this thesis to calculate the data required to construct enthalpy-entropy diagrams for propellant systems and to investigate their usefulness when applied to the determination of rocket motor performance parameters.

Diagrams which cover a range of mixture ratios bracketing the stoichiometric value are included for the following systems:

(1) Liquid Ammonia and RFNA; (2) Liquid Ammonia and Liquid Ozone; (3) Liquid Hydrogen and Liquid Ozone.

Graphical performance parameter values obtained for the stoichiometric mixture of liquid ammonia and RFNA differed less than two tenths of one percent from the analytical values calculated by the Jet Propulsion Laboratory.

Performance values are determined for chamber pressures of 600 PSIA and 300 PSIA and for exhaust pressures of 14.7 PSIA, 7.65 PSIA, and .147 PSIA.

Because of the extensive calculations required to construct an h-s diagram, the graphical method of analysis is not economical unless a comprehensive study of a propellant is desired. However, if performance values are required over a wide range of boundary conditions, the h-s diagram permits the presentation of a large amount of data in a concise and readily useable form.

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